Journal of Mechanical Science and Technology

  • 제19권9호
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  • Pages.1821-1832
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  • 2005
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  • 1738-494X(pISSN)
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  • 1976-3824(eISSN)
대한기계학회 (The Korean Society of Mechanical Engineers)
권호 표지

Hot- Fire Injector Test for Determination of Combustion Stability Boundaries Using Model Chamber

  • Sohn Chae Hoon (Department of Aerospace Engineering, Chosun University) ;
  • Seol Woo-Seok (Rocket Engine Department, Korea Aerospace Research Institute) ;
  • Shibanov Alexander A. (Research Institute of Chemical Machine Building (NIICHIMMASH)) ;
  • Pikalov Valery P. (Research Institute of Chemical Machine Building (NIICHIMMASH))
  • 발행 : 2005.09.01
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초록

This study realizes the conceptual method to predict combustion instability in actual full-scale combustion chamber of rocket engines by experimental tests with model (sub-scale) chamber. The model chamber was designed based on the methodologies proposed in the previous work regarding geometrical dimensions and operating conditions, and hot-fire test procedures were followed to obtain stability boundaries. From the experimental tests, two instability regions are presented by the parameters of combustion-chamber pressure and mixture (oxidizer/fuel) ratio, which are customary for combustor designers. It is found that instability characteristics in the chamber with the adopted jet injectors can be explained by the correlation between the characteristic burning or mixing time and the characteristic acoustic time: In each instability region, dynamic behaviors of flames are investigated to verify the hydrodynamically-derived characteristic lengths of the jet injectors. Large-amplitude pressure oscillation observed in upper instability region is found to be generated by lifted-off flames.

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참고문헌

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